US11015452B2 - Gas turbine blade - Google Patents

Gas turbine blade Download PDF

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Publication number
US11015452B2
US11015452B2 US15/235,568 US201615235568A US11015452B2 US 11015452 B2 US11015452 B2 US 11015452B2 US 201615235568 A US201615235568 A US 201615235568A US 11015452 B2 US11015452 B2 US 11015452B2
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US
United States
Prior art keywords
gas turbine
trench
blade
turbine blade
film cooling
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Active, expires
Application number
US15/235,568
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English (en)
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US20170044905A1 (en
Inventor
Jong Hoon Park
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Doosan Heavy Industries and Construction Co Ltd
Original Assignee
Doosan Heavy Industries and Construction Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
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Assigned to DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD. reassignment DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: PARK, JONG HOON
Publication of US20170044905A1 publication Critical patent/US20170044905A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/12—Two-dimensional rectangular
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/22—Three-dimensional parallelepipedal
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • Exemplary embodiments of the present invention relate to a gas turbine blade and, more particularly, to a gas turbine blade capable of improving cooling efficiency of a blade part and having improved durability by forming a trench part of a film cooling unit for cooling the blade part at a tip of a film cooling hole part.
  • gas turbines are mainly used as one of power sources for rotating generators in power plants, etc.
  • Such a gas turbine includes a compressor, a combustor, and a turbine.
  • the high-temperature compressed gas generated by the combustor flows into the turbine.
  • the blades of the turbine rotate while the high-temperature and high-pressure gas introduced into the turbine is expanded, and thus a rotor connected to the blades rotates so as to generate electric power.
  • the gas expanded in the turbine is discharged to the outside or is discharged to the outside via a cogeneration plant.
  • the film cooling method protects the blade from hot gas by forming holes on the surface of the blade and forming an air film on the surface of the blade using cooling air introduced into the blade.
  • a gas turbine blade includes a blade part, a root part formed at a radial inner end of the blade part while being coupled to a rotor, and a film cooling unit formed on the blade part that cools the blade part, wherein the film cooling unit includes a film cooling hole part formed on a surface of the blade part that cools the surface of the blade part, and a trench part formed at a tip of the film cooling hole part.
  • the tube expansion portion may extend so as to be inclined downward toward the trench part from an extended end of the flow portion.
  • the tube expansion portion may have an opened surface formed in a polygonal shape.
  • the trench part may have a smaller width than a width of a tube expansion portion.
  • the film cooling hole part may be opened toward a center portion of the trench part.
  • the cooling air When cooling air is supplied to a region of the trench part, the cooling air may be ejected toward a center of the trench part through the film cooling hole part, and then branched into both left and right sides to move, so as to perform cooling.
  • the blade part may include a leading edge facing an introduction side of fluid, a trailing edge facing a discharge side of fluid, and first and second surfaces connecting the leading edge to the trailing edge, and the film cooling unit may be formed on the first surface.
  • the film cooling unit may include a plurality of film cooling units formed on the first surface so as to be spaced by a predetermined distance in a radial direction of the blade part.
  • the film cooling hole part formed in the film cooling unit may be formed by coating a film.
  • the trench part may be formed by masking.
  • the root part may include a platform part formed at the radial inner end of the blade part, and a dovetail part formed at a radial inner end of the platform part while being coupled to the rotor.
  • FIG. 1 is a perspective view illustrating a gas turbine blade according to an embodiment of the present invention
  • FIG. 2 is a perspective view illustrating another arrangement of a film cooling unit formed in the gas turbine blade according to an embodiment of the present invention
  • FIG. 3 is an enlarged view illustrating portion “A” of FIG. 1 ;
  • FIG. 4 is a side cross-sectional view illustrating portion “A” of FIG. 1 ;
  • FIG. 5 is an enlarged view illustrating portion “B” of FIG. 3 ;
  • FIG. 6 is a perspective view illustrating a gas turbine blade according to another embodiment of the present invention.
  • FIG. 7 is a perspective view illustrating arrangement of a film cooling unit formed in the gas turbine blade according to another embodiment of the present invention.
  • the terms used herein are defined as follows.
  • the “axially (axial direction)” refers to a longitudinal direction of a rotary shaft such as a rotor of a gas turbine
  • the “radially (radial direction)” refers to a direction oriented from the center of the rotary shaft to the outer peripheral surface thereof, or a direction opposite to the same.
  • the “circumferentially (circumferential direction)” refers to a direction around the rotary shaft.
  • the rotor is rotatably installed in the casing.
  • the casing (not shown) is divided into an upper casing and a lower casing, and the upper and lower casings are assembled and coupled to each other.
  • the casing accommodates the rotor and a bucket assembly therein, and serves to block or protect inter components from external impact or foreign substances.
  • the rotor serves as a rotary shaft, and both ends of the rotor may be rotatably supported by bearings.
  • Accommodation parts for accommodating dovetail parts 220 of root parts 200 to be described later are evenly spaced along the outer peripheral surface of the rotor in the tangential direction of the rotor. That is, each accommodation part is formed at the radial outer end of the rotor so as to have a certain depth in the axial direction of the rotor.
  • the rotor wheel may have a disc or flange shape so as to protrude radially outward from the outer peripheral surface of the rotor.
  • the blade part 100 of the gas turbine blade includes a first surface 130 , a second surface 140 , a leading edge 150 , and a trailing edge 160 .
  • reference numeral 110 refers to the radial inner end of the blade part 100
  • reference numeral 120 refers to the radial outer end of the blade part 100 .
  • the root part 200 is formed at the radial inner end 110 of the blade part 100 .
  • the blade is coupled to the rotor by the root part 200 .
  • the film cooling unit 300 of the gas turbine blade according to an embodiment of the present invention is formed on the first surface 130 .
  • a film cooling unit 300 of a gas turbine blade may be additionally and circumferentially formed on a portion of a platform part 210 for cooling the surface thereof, as well as a blade part 100 .
  • the film cooling unit 300 may include a plurality of film cooling units which are formed on a radial outer end 212 of the platform part 210 so as to be spaced by a predetermined distance.
  • the gas turbine blade may be inhibited from being damaged due to hot gas by cooling the blade part 100 and the platform part 210 , and it is possible to increase the service life of the gas turbine blade and reduce maintenance costs therefore.
  • the film cooling unit 300 of the gas turbine blade includes a film cooling hole part 310 and a trench part 320 .
  • the film cooling hole part 310 allows cooling air to be supplied to the surface of the blade part 100 for cooling the surface of the blade part 100 .
  • the film cooling hole part 310 may be formed by coating a film on the surface of the blade part 100 , but the present invention is not limited thereto.
  • the trench part 320 is formed at the tip of the film cooling hole part 310 .
  • the trench part 320 may be formed by masking, but the present invention is not limited thereto.
  • the trench part 320 may be formed by machining such as grinding, if necessary.
  • the trench part 320 is formed at the tip of the film cooling hole part 310 , which is a side opposite to the direction from which the hot gas is introduced.
  • Cooling air for cooling the surface of the blade part 100 flows into the cooling groove portion 311 . That is, the cooling groove portion 311 communicates with a cooling passage formed in the blade part 100 .
  • the cooling groove portion 311 and the flow portion 312 may have the same diameter, but the present invention is not limited thereto.
  • the tube expansion portion 313 has a cross-sectional area that is increased toward the surface of the blade part 100 from the tip of the flow portion 312 .
  • the tube expansion portion 313 has a predetermined inclination angle ( ⁇ ).
  • Cooling is performed while after cooling air is moved from the trench part 320 to the front center portion thereof, it is branched into the left and the right and is moved. Therefore, the path of cooling air is simple in the course of flow, and the cooling air is consistently maintained in the state in which it is in contact with the bottom of the trench part. Consequently, a cooling effect is more uniformly maintained in the whole section of the trench part 320 .
  • the film cooling hole part 310 Since the film cooling hole part 310 is opened toward the center portion of the trench part 320 , the path in which cooling air is moved toward the center of the trench part 320 is always maintained. The movement direction of cooling air is significant to improve the cooling performance of the trench part 320 . Accordingly, when the film cooling hole part 310 is opened toward the center portion of the trench part 320 , it is possible to more improve cooling efficiency according to movement of cooling, compared to when the film cooling hole part 310 is opened toward the side of the trench part.
  • the trench part 320 of the film cooling unit 300 of the gas turbine blade has a height (H) equal to the thickness of the coating layer 170 of the blade part 100 .
  • the costs and time required to manufacture the gas turbine blade can be reduced.
  • the trench part 320 of the film cooling unit 300 of the gas turbine blade according to an embodiment of the present invention has the same width (W) and height.
  • cooling air may completely cover the whole surface of the blade part so as to form a cooling air film, thereby increasing cooling efficiency.
  • portion “C” is located between portions “A” and “B”, a dead zone in which cooling is not performed is minimized in portion “C”.
  • a trench part of a film cooling unit for cooling a blade part is formed at the tip of a film cooling hole part.
  • a gas turbine can have improved efficiency.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US15/235,568 2015-08-13 2016-08-12 Gas turbine blade Active 2038-06-15 US11015452B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR1020150114631A KR101839656B1 (ko) 2015-08-13 2015-08-13 가스터빈 블레이드
KR10-2015-0114631 2015-08-13

Publications (2)

Publication Number Publication Date
US20170044905A1 US20170044905A1 (en) 2017-02-16
US11015452B2 true US11015452B2 (en) 2021-05-25

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ID=56694001

Family Applications (1)

Application Number Title Priority Date Filing Date
US15/235,568 Active 2038-06-15 US11015452B2 (en) 2015-08-13 2016-08-12 Gas turbine blade

Country Status (4)

Country Link
US (1) US11015452B2 (ko)
EP (1) EP3133243B1 (ko)
KR (1) KR101839656B1 (ko)
WO (1) WO2017026875A1 (ko)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102117430B1 (ko) 2018-11-14 2020-06-01 두산중공업 주식회사 블레이드의 냉각성능 향상 구조와 이를 포함하는 블레이드 및 가스터빈
CN109653806B (zh) * 2019-01-03 2019-10-29 北京航空航天大学 一种涡轮导叶非尾缘扩张型缝冷却结构
EP4108883A1 (en) 2021-06-24 2022-12-28 Doosan Enerbility Co., Ltd. Turbine blade and turbine
KR102623227B1 (ko) 2021-06-24 2024-01-10 두산에너빌리티 주식회사 터빈 블레이드 및 이를 포함하는 터빈
CN113901613B (zh) * 2021-10-20 2024-04-26 中国航发沈阳黎明航空发动机有限责任公司 一种具有冷却结构转子减振器的设计方法

Citations (10)

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US6234755B1 (en) * 1999-10-04 2001-05-22 General Electric Company Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture
US20100040478A1 (en) * 2008-08-14 2010-02-18 United Technologies Corp. Cooled Airfoils and Gas Turbine Engine Systems Involving Such Airfoils
US20110305583A1 (en) * 2010-06-11 2011-12-15 Ching-Pang Lee Component wall having diffusion sections for cooling in a turbine engine
WO2011156805A1 (en) 2010-06-11 2011-12-15 Siemens Energy, Inc. Film cooled component wall in a turbine engine
US20120076644A1 (en) * 2010-09-23 2012-03-29 Zuniga Humberto A Cooled component wall in a turbine engine
JP2012082700A (ja) 2010-10-07 2012-04-26 Hitachi Ltd タービン翼の冷却孔加工方法
EP2615245A2 (en) 2012-01-13 2013-07-17 General Electric Company Film cooled turbine airfoil having trench segments on the exterior surface
US20130183166A1 (en) * 2012-01-13 2013-07-18 General Electric Company Airfoil
KR101434926B1 (ko) 2010-07-09 2014-08-27 가부시키가이샤 아이에이치아이 터빈 블레이드, 및 엔진 부품
US20150107798A1 (en) * 2013-10-18 2015-04-23 Rolls-Royce Deutschland Ltd & Co Kg Unknown

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US8916005B2 (en) * 2007-11-15 2014-12-23 General Electric Company Slurry diffusion aluminide coating composition and process
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US9188012B2 (en) * 2012-05-24 2015-11-17 General Electric Company Cooling structures in the tips of turbine rotor blades

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Publication number Priority date Publication date Assignee Title
US6234755B1 (en) * 1999-10-04 2001-05-22 General Electric Company Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture
US20100040478A1 (en) * 2008-08-14 2010-02-18 United Technologies Corp. Cooled Airfoils and Gas Turbine Engine Systems Involving Such Airfoils
US8105030B2 (en) * 2008-08-14 2012-01-31 United Technologies Corporation Cooled airfoils and gas turbine engine systems involving such airfoils
US20110305583A1 (en) * 2010-06-11 2011-12-15 Ching-Pang Lee Component wall having diffusion sections for cooling in a turbine engine
WO2011156805A1 (en) 2010-06-11 2011-12-15 Siemens Energy, Inc. Film cooled component wall in a turbine engine
US8608443B2 (en) * 2010-06-11 2013-12-17 Siemens Energy, Inc. Film cooled component wall in a turbine engine
KR101434926B1 (ko) 2010-07-09 2014-08-27 가부시키가이샤 아이에이치아이 터빈 블레이드, 및 엔진 부품
US20120076644A1 (en) * 2010-09-23 2012-03-29 Zuniga Humberto A Cooled component wall in a turbine engine
US9028207B2 (en) * 2010-09-23 2015-05-12 Siemens Energy, Inc. Cooled component wall in a turbine engine
EP2619443A2 (en) 2010-09-23 2013-07-31 Siemens Energy, Inc. Cooled component wall in a turbine engine
JP2012082700A (ja) 2010-10-07 2012-04-26 Hitachi Ltd タービン翼の冷却孔加工方法
US20130183166A1 (en) * 2012-01-13 2013-07-18 General Electric Company Airfoil
US8870536B2 (en) * 2012-01-13 2014-10-28 General Electric Company Airfoil
EP2615245A2 (en) 2012-01-13 2013-07-17 General Electric Company Film cooled turbine airfoil having trench segments on the exterior surface
US20150107798A1 (en) * 2013-10-18 2015-04-23 Rolls-Royce Deutschland Ltd & Co Kg Unknown
EP2889451A1 (de) 2013-10-18 2015-07-01 Rolls-Royce Deutschland Ltd & Co KG Vorrichtung zur Kühlung einer Wandung eines Bauteils

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Office Action dated Aug. 31, 2017 in Korean Application No. 10-2015-0114631.

Also Published As

Publication number Publication date
KR101839656B1 (ko) 2018-04-26
US20170044905A1 (en) 2017-02-16
WO2017026875A1 (ko) 2017-02-16
EP3133243B1 (en) 2021-04-28
KR20170020008A (ko) 2017-02-22
EP3133243A1 (en) 2017-02-22

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